Technique applied in electrical power distribution for Satellite Launch Vehicle
نویسندگان
چکیده
منابع مشابه
Nonlinear Optimal Control Techniques Applied to a Launch Vehicle Autopilot
This paper presents an application of the nonlinear optimal control techniques to the design of launch vehicle autopilots. The optimal control is given by the solution to the Hamilton-Jacobi-Bellman (HJB) equation, which in this case cannot be solved explicity. A method based upon Successive Galerkin Approximation (SGA), is used to obtain an approximate optimal solution. Simulation results invo...
متن کاملSelf-configuring Network for Launch Vehicle and Satellite Avionics
Under an Air Force Phase II SBIR contract, Microcosm is developing a self-configuring avionics network, scheduled for test on a sounding rocket in late 2003 or early 2004. This system is extendable to spacecraft avionics and housekeeping functions, enabling true plug-and-play capability.
متن کاملfault location in power distribution networks using matching algorithm
چکیده رساله/پایان نامه : تاکنون روشهای متعددی در ارتباط با مکان یابی خطا در شبکه انتقال ارائه شده است. استفاده مستقیم از این روشها در شبکه توزیع به دلایلی همچون وجود انشعابهای متعدد، غیر یکنواختی فیدرها (خطوط کابلی، خطوط هوایی، سطح مقطع متفاوت انشعاب ها و تنه اصلی فیدر)، نامتعادلی (عدم جابجا شدگی خطوط، بارهای تکفاز و سه فاز)، ثابت نبودن بار و اندازه گیری مقادیر ولتاژ و جریان فقط در ابتدای...
Materials for Launch Vehicle Structures
This chapter concerns materials for expendable and reusable launch vehicle (LV) structures. An emphasis is placed on applications and design requirements, and how these requirements are met by the optimum choice of materials. Structural analysis and qualification strategies, which cannot be separated from the materials selection process, are described. A launch vehicle is an airborne system tha...
متن کاملTrajectory Optimization for a Multistage Launch Vehicle Using Nonlinear Programming
This work is an example of application of nonlinear programming to a problem of three-dimensional trajectory optimization for multistage launch vehicles for geostationary orbit missions. The main objective is to minimize fuel consumption or equivalently to maximize the payload. The launch vehicle considered here, Europa-II, consists of 5 thrust phases and 2 coast phases. Major parameters of the...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Journal of Aerospace Technology and Management
سال: 2010
ISSN: 2175-9146
DOI: 10.5028/jatm.2010.02038410